低转速条件下的弹丸飞行稳定性分析

Flight Stability Analysis of Projectile at Low Speed

为了解决制导炮弹引信试验成本高、研制进度慢、试验条件复杂等问题,以制式榴弹为原型设计了模拟试验弹,用于模拟引信的发射环境。由于试验弹转速较低,在不采用尾翼的条件下,出炮口距离200~300 m内,弹丸是否飞行稳定,是一个需要重点考虑的问题。飞行中的弹丸,由于阻力方向与质心运动方向不一致,导致合力不一定通过质心,迫使弹体在空中翻转,所以弹体的旋转速度和气动外形设计是弹体飞行稳定的必要条件。通过对弹丸在一定距离内的飞行稳定性数值计算,用数值计算结果进行稳定性仿真分析,进而说明数值仿真计算对弹丸气动外形设计可以提供有效参考。

To solve the problems of high cost,slow development speed and complex test conditions of the guided projectile fuze,a simulation test projectile was designed based on the standard grenade,which is used to simulate the launching environment of the fuze. Since the speed of test projectile is low under the condition of not using the tail fin,the flying stability of the projectile within the muzzle distance from200 meters to 300 meters needs to be considered. In flight,because the resistance direction is not consistent with the direction of the center of mass movement,the resultant force does not necessarily pass through the centroid,forcing the projectile to rotate in the air,so the rotation speed and aerodynamic shape design of the projectile body is the necessary condition for the projectile flight stability. The flight stability of the projectile within a certain distance is calculated,the stability simulation analysis is carried out with the numerical calculation results,and the numerical simulation calculation can provide effective reference for the projectile aerodynamic shape design.